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Customer bleed air pressure loss reduction

a technology for reducing customer bleed air pressure and reducing the cost of bleed air, which is applied in the direction of efficient propulsion technology, machines/engines, stators, etc., can solve the problems of reducing the efficiency of associated aircraft, unable to provide sufficient air, and raising challenges near the ports, so as to reduce the cross-sectional flow and increase the cross-sectional flow area

Active Publication Date: 2018-11-06
RTX CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The solution significantly reduces pressure loss and enhances the efficiency of air delivery to aircraft systems, ensuring consistent air supply without decreasing engine performance.

Problems solved by technology

The pressure loss near the ports raises challenges with regard to providing sufficient air without decreasing the efficiency of the associated aircraft.

Method used

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  • Customer bleed air pressure loss reduction
  • Customer bleed air pressure loss reduction
  • Customer bleed air pressure loss reduction

Examples

Experimental program
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Effect test

embodiment 118

[0044]FIG. 4 shows a diffuser embodiment 118 wherein an outer shroud 58 of the diffuser ends upstream of a radially inner shroud 54. As shown, vanes 56 extend between the shroud walls 54 and 58.

[0045]The duct 50 communicates with an opening 42. Further details of this duct will be disclosed below.

[0046]FIG. 5 shows a portion of the diffuser 118. As shown, the outer shroud is cut upstream, at locations 58 associated with the opening 42, but otherwise extends forwardly 158 to the location of the prior art diffuser as shown, for example, in FIG. 3. In embodiments, there are plural ducts 50 and openings 42, and the cutaway locations 58 are associated with each opening 42.

[0047]Cutting away the diffuser at the areas 58 associated with the opening 42 dramatically reduces pressure loss.

[0048]FIG. 6A shows an arrangement wherein the ports 64 and 66 communicate with a common conduit 62, which then communicates downstream to various uses for air on the aircraft. Ports 64 and 66 are spaced by ...

embodiment 150

[0054]FIG. 7B shows the use of the insert 182 in a somewhat alternative duct embodiment 150. As can be seen from FIG. 7A, the insert and duct in the FIG. 7A embodiment bend at 88, while the FIG. 7B embodiment extends generally linearly.

[0055]As shown in FIG. 7B, an upstream flow cross-sectional area A1 defined between the outer periphery of the insert 182 and the inner periphery of the duct 150 is much smaller than a downstream cross-sectional flow area A2 again defined between the insert and the inner wall of the duct. This creates a venturi effect.

[0056]As can be seen from the FIGS. 7A and 7B, the insert ends at an intermediate location within the ducts 50 or 150, and will end before the outlet 400 of the duct 50, which communicates into other portions of the air supply system.

[0057]FIG. 7C shows features of the FIG. 7A or 7B embodiments wherein insert holders 90 mount the insert within the duct 50. In this embodiment there are three insert holders, each spaced by 120°.

[0058]FIG. ...

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PUM

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Abstract

A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.

Description

BACKGROUND OF THE INVENTION[0001]This application relates to a system for reducing pressure loss on bleed air systems for tapping air away from a gas turbine engine for use on an associated aircraft.[0002]Gas turbine engines for use on aircraft typically include a fan delivering air into a compressor. Air from the compressor is directed into a combustion section where it is mixed with fuel and burned. Products of this combustion pass downstream over turbine rotors, causing them to rotate and power the fan and compressor rotors.[0003]When gas turbine engines are utilized on aircraft, they are also the source of air for various uses on the aircraft. As examples, cabin air, cooling air, or air for any number of other applications are tapped from the gas turbine engine.[0004]Typically, air that has been at least partially compressed is utilized. In many applications, the air is initially taken from a port downstream of the entire compressor section, and upstream of the combustion sectio...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F02C6/08F01D9/06F01D9/02F02C7/18F02C9/18
CPCF02C6/08F01D9/023F01D9/065F02C7/185F02C9/18Y02T50/675F05D2260/601F05D2270/17F05D2270/301Y02T50/60
Inventor WANG, CHENG-ZHANGPHILLIPS, THOMAS G.CLOUD, DAVID F.MUNSELL, PETER M.
Owner RTX CORP
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